Having Means To Effect A Variable Bypass Ratio Patents (Class 60/226.3)
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Patent number: 8151551Abstract: A nozzle for use in a gas turbine engine includes nozzle doors coupled with a fan nacelle wherein the nozzle doors move in unison between a plurality of positions to influence a bypass airflow through a fan bypass passage. A linkage connects the nozzle doors and an actuator. A louver section coupled with the linkage moves in unison with the nozzle doors between a plurality of louver positions to direct a portion of the bypass airflow in a selected direction.Type: GrantFiled: October 12, 2006Date of Patent: April 10, 2012Assignee: United Technologies CorporationInventor: Edward B. Pero
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Publication number: 20120073262Abstract: An air discharging device (20) for an aircraft turbine engine, comprising at least one door (24) displaceable between an open and a closed position of a corresponding orifice (30) and comprising two valves (26, 28), which delimit between them a conduit (68) for guiding a portion (74) of the secondary flow (76) outwards in the downstream direction, and which are integral with each other and are hinged around a pivot axis (58), so that in said open position, the upstream end of said internal valve (26) protrudes from the inner side relative to the internal surface (12), the downstream end of said external valve (28) protrudes from the external side relative to the external surface (14), and said internal valve (26) is spaced away from the fixed structure (22) so that an air passage exists downstream of said internal valve (26), between the latter and said fixed structure (22).Type: ApplicationFiled: September 19, 2011Publication date: March 29, 2012Applicant: Airbus Operations (S.A.S.)Inventors: Guillaume BULIN, Thierry Surply
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Publication number: 20120073263Abstract: A nacelle assembly for a high-bypass gas turbine engine includes a fan variable area nozzle axially movable relative the fan nacelle to define an auxiliary port to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation.Type: ApplicationFiled: December 8, 2011Publication date: March 29, 2012Inventors: Gregory A. Kohlenberg, Sean P. Zamora
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Publication number: 20120067025Abstract: An adjustable bloom mixer for a turbofan engine for setting a mixing ratio, adapted to the respective flight condition, between cold airflow in the bypass duct and hot airflow in the core flow duct includes an air-guiding element (13) arranged upstream of a thin-walled, corrugated part (6b) of the bloom mixer (6) for branching off a cold partial airflow and/or a hot partial airflow from the bypass duct and from the core flow duct of the engine. An air control device (14) is assigned to the air-guiding element (13) for leading the branched-off cold airflow or hot airflow along the inner surface and/or the outer surface of the bloom mixer (6) in order to deflect its corrugated part (6b) radially inwards or outwards on the basis of a temperature difference between an inner and an outer surface effected by the hot and/or cold partial airflow.Type: ApplicationFiled: September 13, 2011Publication date: March 22, 2012Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KGInventor: Robert THIES
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Publication number: 20120055137Abstract: A fan portion of a dual flow turbojet engine including a plurality of fan blades, a disk supporting the blades and configured to be rotated relative to a stator portion of the fan, along a longitudinal axis of the fan, and a system for setting the angle of attack associated with each fan blade, the systems configured such that the angle of attack of each blade varies according to a same setting law according to the angular position of the blade relative to the stator portion, along the longitudinal axis, the same setting law being periodic with a period of P=360°/n, where n is an integer at least equal to 1.Type: ApplicationFiled: February 25, 2010Publication date: March 8, 2012Applicant: SNECMAInventors: Philippe Pierre Vincent Bouiller, Stephane Rousselin
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Patent number: 8127532Abstract: A variable area nozzle system for a gas turbine engine includes a fan duct inner wall, a fan duct outer wall disposed in radially spaced relation to the fan duct inner wall, and a fan nozzle. The fan nozzle defines at least a portion of the fan duct outer wall and includes a nozzle aft edge. The fan duct inner wall and the nozzle aft edge collectively define a fan duct nozzle throat area. The fan nozzle is configured to pivot about a pivot axis that may be oriented transversely relative to a longitudinal axis of the gas turbine engine. The fan nozzle may be pivoted from a stowed position to a deployed position in order to vary the fan duct nozzle throat area.Type: GrantFiled: November 26, 2008Date of Patent: March 6, 2012Assignee: The Boeing CompanyInventor: Mark E. Howe
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Patent number: 8127531Abstract: A variable area nozzle system for a turbofan gas turbine engine comprises a fan duct inner wall, a fan duct outer wall and a fan nozzle. The fan duct outer wall is disposed in radially-spaced relation to the fan duct inner wall. The fan nozzle defines at least a portion of the fan duct outer wall and has a nozzle aft edge defining a fan duct throat area relative to the fan duct inner wall. The fan nozzle is configured to move outwardly relative to the longitudinal axis during axial aft translation thereof in order to vary the fan duct throat area.Type: GrantFiled: November 11, 2008Date of Patent: March 6, 2012Assignee: The Boeing CompanyInventor: Dean L. Parham
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Patent number: 8127528Abstract: A core engine of a variable cycle gas turbine engine includes a low pressure spool for generating streams of bypass air and pressurized air, and a high pressure spool for further pressurizing the stream of pressurized air to generate streams of combustion air and supercharged auxiliary air. A peripheral case surrounds the engine case to form a peripheral duct. An auxiliary combustor and propulsor are positioned within the peripheral duct. A bleed duct extends from the high pressure spool to the auxiliary combustor. Variable ductwork directs airflow through the bleed duct and peripheral duct in two modes. A first mode comprises directing the stream of auxiliary air to the auxiliary combustor, and directing stream of inlet air through the peripheral duct. A second mode comprises directing the stream of auxiliary air into the stream of bypass air, and preventing inlet air from entering the peripheral duct.Type: GrantFiled: February 26, 2008Date of Patent: March 6, 2012Assignee: United Technologies CorporationInventor: Gary D. Roberge
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Publication number: 20120023901Abstract: A high-bypass gas turbine engine includes a variable area fan nozzle with an acoustic system having an acoustic impedance.Type: ApplicationFiled: July 27, 2010Publication date: February 2, 2012Inventors: Jonathan Gilson, Andre M. Hall, Oliver V. Atassi, Ramons A. Reba
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Patent number: 8104262Abstract: A gas turbine engine system includes a nozzle having a plurality of positions for altering a discharge flow received through the nozzle from a gas turbine engine fan bypass passage. The nozzle is integrated with a thrust reverser having a stowed position and a deployed position to divert the discharge flow and generate a reverse thrust force. At least one actuator is coupled with the nozzle and the thrust reverser to selectively move the nozzle between the plurality of positions and to move the thrust reverser between the stowed position and the deployed position.Type: GrantFiled: October 12, 2006Date of Patent: January 31, 2012Assignee: United Technologies CorporationInventor: Richard M. Marshall
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Publication number: 20120011827Abstract: A bleed air outlet provided in the bypass duct of a turbofan engine includes a bleed air tube protruding into the bypass duct and a cover having a plurality of air outlet openings provided in the top of the cover, with the cover being conceived as an elongate, essentially oval, shell-like aerodynamic fairing element (3) which, while extending in the longitudinal direction of the bypass duct, is provided with a longitudinally convexly curved and transversely essentially straight top (10) and sidewalls (11) arcuately extending from the latter to an inner bypass duct wall. Such a design of the bleed air outlet reduces pressure losses, acoustic emissions and vibrations in the bypass duct.Type: ApplicationFiled: July 14, 2011Publication date: January 19, 2012Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KGInventor: Carsten CLEMEN
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Publication number: 20120011825Abstract: A bypass gas turbine engine includes a variable area fan nozzle with a leading edge region that defines an increased airfoil leading edge radius.Type: ApplicationFiled: July 19, 2010Publication date: January 19, 2012Inventors: Andre M. Hall, Oliver V. Atassi, Jonathan Gilson
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Patent number: 8096105Abstract: A plurality of hatches are distributed on the rear periphery of an engine cowl. The hatches are opened only when turbojet engine power is greater than cruising power. In an open position, the hatches draw hot air jets passing through an intermediate chamber before ejecting the jets through longitudinally-distributed communication components.Type: GrantFiled: October 17, 2006Date of Patent: January 17, 2012Assignee: Airbus Operations SASInventor: Alain Porte
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Patent number: 8091334Abstract: An inner core cowl baffle assembly for a turbofan engine assembly is provided. The engine assembly includes a core gas turbine engine, a core cowl which circumscribes the core gas turbine engine, a nacelle positioned radially outward from the core cowl, and a fan nozzle duct defined between the core cowl and the nacelle. The inner core cowl baffle assembly includes an inner core cowl baffle, and an actuator assembly configured to vary the throat area of the fan nozzle duct by selectively repositioning the inner core cowl baffle with respect to the core cowl.Type: GrantFiled: January 26, 2011Date of Patent: January 10, 2012Assignee: General Electric CompanyInventors: Thomas Ory Moniz, Jorge Francisco Seda, Robert Joseph Orlando
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Patent number: 8082727Abstract: A gas turbine propulsion system comprises a turbofan engine, a peripheral duct, an annular frame, an auxiliary turbine and an auxiliary fan. The turbofan engine is configured to produce bypass air and combustion air. The bypass air flows through a bypass duct and the combustion air flows through a core engine. The peripheral duct surrounds the turbofan engine and is configured to selectively receive peripheral inlet air. The annular frame is disposed aft of the bypass duct and the peripheral duct, and is rotatable to alternately guide the bypass air out the bypass duct or the peripheral duct. The auxiliary turbine is connected to an aft end of the core engine and is configured to receive the combustion air. The auxiliary fan is connected to the auxiliary turbine and is configured to receive airflow from the peripheral duct.Type: GrantFiled: February 26, 2008Date of Patent: December 27, 2011Assignee: United Technologies CorporationInventor: Gary D. Roberge
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Publication number: 20110302907Abstract: A nacelle assembly for a high-bypass gas turbine engine includes a variable area fan nozzle in communication with a fan bypass flow path. An actuator assembly is operable to move a second fan nacelle section relative to a first fan nacelle section to vary a fan nozzle exit area and adjust fan bypass airflow, the actuator assembly extends at least partially into the fan bypass flow path.Type: ApplicationFiled: June 11, 2010Publication date: December 15, 2011Inventor: Michael J. Murphy
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Patent number: 8074440Abstract: A turbofan engine includes a fan variable area nozzle includes having a first fan nacelle section and a second fan nacelle section movably mounted relative the first fan nacelle section. The second fan nacelle section axially slides aftward relative to the fixed first fan nacelle section to change the effective area of the fan nozzle exit area.Type: GrantFiled: August 23, 2007Date of Patent: December 13, 2011Assignee: United Technologies CorporationInventors: Gregory A. Kohlenberg, Sean P. Zamora
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Publication number: 20110289900Abstract: A gas turbine engine system includes a first nozzle section associated with a gas turbine engine bypass passage and a second nozzle section that includes a plurality of positions relative to the first nozzle section. In at least one of the positions, there is a gap between the first nozzle section and the second nozzle section. A movable door between the first nozzle section and the second nozzle section selectively opens or closes the gap.Type: ApplicationFiled: August 1, 2011Publication date: December 1, 2011Inventor: Alfred M. Stern
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Patent number: 8028513Abstract: An engine for powering a vehicle, such as a military aircraft or a commercial aircraft, is provided. The engine broadly comprises a main core with a plurality of spools with each spool having a plurality of compressor blades and a plurality of turbine blades attached thereto. One of the spools has a first set of fan blades attached thereto. The engine further has a variable bypass turbine fan formed by a second set of fan blades. The second set of fan blades is arranged outboard of the main core. The second set of fan blades may be decoupled from the first set of fan blades.Type: GrantFiled: October 26, 2007Date of Patent: October 4, 2011Assignee: United Technologies CorporationInventors: James W. Norris, Craig A. Nordeen, Bernard J. Raver
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Patent number: 8020365Abstract: A gas turbine engine comprising a compressor, a combustion chamber, and at least two turbines mounted oppositely to the combustion chamber, such that the gas turbine engine is capable of generating multidirectional thrust.Type: GrantFiled: June 13, 2008Date of Patent: September 20, 2011Inventor: Kamyar Brothers
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Patent number: 8015996Abstract: A gas turbine engine air valve assembly has first and second valving elements. The second element is rotatable about a first axis relative to the first element. The rotation controls a flow of air through the first and second elements. An actuator is coupled by a linkage to the second element. The linkage includes a spindle having a first portion coupled to the actuator to rotate the spindle about a second axis. A guided spherical bearing couples a second portion of the spindle to the second element.Type: GrantFiled: April 28, 2005Date of Patent: September 13, 2011Assignee: United Technologies CorporationInventors: Andreas Sadil, William W. Pankey
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Patent number: 8001763Abstract: A turbine engine provides a spool supporting a turbine. The spool is arranged in a core nacelle and includes a thrust bearing. A fan is arranged upstream from the core nacelle and is coupled to the spool. A fan nacelle surrounds the fan and core nacelle and provides a bypass flow path that includes a fan nozzle exit area. A flow control device is adapted to effectively change the fan nozzle exit area. A controller is programmed to monitor the thrust bearing and command the flow control device in response to an undesired load on the thrust bearing. Effectively changing the fan nozzle exit area with the flow control device actively manages the bearing thrust load to desired levels.Type: GrantFiled: September 16, 2010Date of Patent: August 23, 2011Assignee: United Technologies CorporationInventors: Zbigniew M. Grabowski, Michael Winter
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Publication number: 20110167791Abstract: A gas turbine engine is disclosed having a fan system with a front stage fan rotor and an aft fan rotor coupled to a low-pressure turbine, a core having a compressor coupled to a high-pressure turbine, an annular inner bypass passage and an annular outer bypass passage. The aft fan rotor has a row of aft fan blades having an arcuate splitter that forms a portion of an inner flow passage and an outer flow passage wherein the aft fan blade pressurizes an inner flow and an outer flow and wherein the fan tip pressure ratio can be changed while the air flow into the front stage fan rotor is held substantially constant.Type: ApplicationFiled: December 21, 2009Publication date: July 14, 2011Inventors: James Edward Johnson, Brandon Flowers Powell
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Publication number: 20110167792Abstract: An adaptive gas turbine engine is disclosed having a convertible fan system adapted to have a variable fan pressure ratio while the air flow into the convertible fan system remains substantially constant and an adaptive core having a compressor capable of maintaining a substantially constant core pressure ratio while a core airflow flow rate is varied.Type: ApplicationFiled: December 21, 2009Publication date: July 14, 2011Inventors: JAMES EDWARD JOHNSON, Brandon Flowers Powell
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Publication number: 20110167790Abstract: A nacelle assembly for a high-bypass gas turbine engine includes a fan nacelle that includes a first fan nacelle section and a second fan nacelle section, the second fan nacelle section movable relative to the first fan nacelle section. A cascade array is mounted to the first fan nacelle section for movement relative thereto between a stored position and a deployed position, the stored position locates the cascade array at least partially within the first fan nacelle section.Type: ApplicationFiled: January 13, 2010Publication date: July 14, 2011Inventors: Thomas G. Cloft, Robert L. Gukeisen
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Publication number: 20110154804Abstract: A gas turbine engine is provided having an offtake passage that in one form is capable of extracting a bypass flow from the engine. The airflow traversing the offtake passage is introduced to an exhaust flow of the gas turbine engine through an offtake outlet. The offtake outlet includes an airflow member that is moveable. A nozzle is also provided for exhaust from the gas turbine engine. In one form the nozzle includes moveable duct members. Flows exiting the offtake outlet and the nozzle can be combined after passing the airflow member and the moveable duct members, respectively.Type: ApplicationFiled: December 21, 2010Publication date: June 30, 2011Inventor: David Levi Sutterfield
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Publication number: 20110120080Abstract: A nacelle assembly for a high-bypass gas turbine engine includes a variable area fan nozzle having a first fan nacelle section and a second fan nacelle section. The second fan nacelle section being axially movable relative the first fan nacelle section to define an auxiliary port to vary a fan nozzle exit area and adjust fan bypass airflow, the second fan nacelle section includes at least one cowl with an inner portion, an outer portion and a multiple of stiffeners therebetween to increase a flutter margin.Type: ApplicationFiled: November 24, 2009Publication date: May 26, 2011Inventors: Fred W. Schwark, JR., Oliver V. Atassi, William D. Owen
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Publication number: 20110120082Abstract: A fan assembly having an outer fan system is disclosed, the fan assembly comprising an outer fan first stage and an outer fan second stage both extending radially outward from an arcuate platform.Type: ApplicationFiled: June 8, 2010Publication date: May 26, 2011Inventors: Rollin George Giffin, James Edward Johnson
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Publication number: 20110120081Abstract: A variable area fan nozzle for a high-bypass gas turbine engine includes a first track slider movable relative to the hinge beam along a first interface. A second track slider is movable relative to the first track slider along a second interface that includes a bearing assembly. A VAFN cowl is mounted to the second track slider.Type: ApplicationFiled: November 24, 2009Publication date: May 26, 2011Inventors: Fred W. Schwark, JR., Oliver V. Atassi, William D. Owen
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Publication number: 20110120078Abstract: A variable area fan nozzle for a high-bypass gas turbine engine includes a first track slider movable relative to the hinge beam along a first interface. A second track slider is movable relative to the first track slider along a second interface that is more closely controlled than the first interface. A VAFN cowl is mounted to the second track slider.Type: ApplicationFiled: November 24, 2009Publication date: May 26, 2011Inventors: Fred W. Schwark, JR., Oliver V. Atassi, William D. Owen
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Publication number: 20110120083Abstract: A gas turbine engine comprising an outer fan system is disclosed, having an outer fan first stage having a circumferential row of outer fan first blades, an outer fan second stage having a circumferential row of outer fan second blades located axially aft from the outer fan first stage wherein the outer fan first stage and the outer fan second stage are adapted to rotate with the fan rotor.Type: ApplicationFiled: June 8, 2010Publication date: May 26, 2011Inventors: ROLLIN GEORGE GIFFIN, James Edward Johnson
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Patent number: 7926290Abstract: A gas turbine engine includes a turbomachinery core operable to generating a flow of pressurized combustion gases; a rotating fan adapted to extract energy from the core and generate a first flow of pressurized air; a fan stator assembly connected in flow communication with the fan and operable to vary the first flow of pressurized air while the fan operates at a substantially constant speed; a fan outer duct surrounding the core; and a flade stage comprising a supplementary fan disposed in the fan outer duct and driven by the fan for generating a pressurized bleed air flow.Type: GrantFiled: December 18, 2006Date of Patent: April 19, 2011Assignee: General Electric CompanyInventor: James E. Johnson
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Publication number: 20110072781Abstract: Systems and methods for passively directing aircraft engine nozzle flow are disclosed. One system includes an aircraft nozzle attachable to an aircraft turbofan engine, with the nozzle including a first flow path wall bounding a first flow path and being positioned to receive engine exhaust products, and a second flow path wall bounding a second flow path and being positioned to receive engine bypass air. The first flow path wall is positioned between the first and second flow paths, and the second flow path wall is positioned between the second flow path and an ambient air flow path. Multiple flow passages can be positioned in at least one of the first and second flow path walls to passively direct gas from a corresponding flow path within the flow path wall through the flow path wall to a corresponding flow path external to the flow path wall.Type: ApplicationFiled: December 7, 2010Publication date: March 31, 2011Applicant: The Boeing CompanyInventors: Stanley F. Birch, Alexander N. Secundov, Dmitriy A. Lyubimov, Konstantin M. Khritov, Vladimir P. Maslov, Aleksey K. Mironov
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Patent number: 7886518Abstract: An inner core cowl baffle assembly for a turbofan engine assembly is provided. The engine assembly includes a core gas turbine engine, a core cowl which circumscribes the core gas turbine engine, a nacelle positioned radially outward from the core cowl, and a fan nozzle duct defined between the core cowl and the nacelle. The inner core cowl baffle assembly includes an inner core cowl baffle, and an actuator assembly configured to vary the throat area of the fan nozzle duct by selectively repositioning the inner core cowl baffle with respect to the core cowl.Type: GrantFiled: November 14, 2006Date of Patent: February 15, 2011Assignee: General Electric CompanyInventors: Thomas Ory Moniz, Jorge Francisco Seda, Robert Joseph Orlando
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Patent number: 7866228Abstract: The invention relates to a device (20) for moving at least one moveable element (19) in a gas turbine engine (1) between a first and a second position. The device includes a linkage (21) that connects a pivotable annular member (18) with the moveable element (19) in such a way that the movement of the moveable element (19) between the two positions is accomplished when the annular member (18) is pivoted. The linkage (21) has a link member (22) connected to the moveable element (19) via a first articulation joint (23). The device also has a support member (24) that supports the link member (22) at a distance from the first articulation joint.Type: GrantFiled: June 7, 2006Date of Patent: January 11, 2011Assignee: Volvo Aero CorporationInventors: Egon Aronsson, Mike Billett
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Publication number: 20110004388Abstract: A control system for a turbofan comprises a variable area nozzle for regulating core flow through the turbofan, an actuator, a temperature sensor, a flight controller and a nozzle control. The actuator is coupled to the variable area nozzle to regulate the core flow by positioning the variable area nozzle. The temperature sensor is positioned in the turbofan to sense a gas path temperature of the core flow. The flight controller is connected to the turbofan to make a thrust demand based on a flight condition of the turbofan. The nozzle control is connected to the flight controller and the actuator for directing the actuator based on the gas path temperature and the flight condition, such that the gas path temperature is controlled by adjusting the variable area nozzle to regulate the core flow while the turbofan meets the thrust demand.Type: ApplicationFiled: July 1, 2009Publication date: January 6, 2011Applicant: UNITED TECHNOLOGIES CORPORATIONInventor: Michael Winter
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Patent number: 7837436Abstract: A method for regulating fluid flow through a gas turbine engine is provided. The method includes coupling an outer fairing to a radially outer duct wall and coupling an inner fairing to a radially inner duct wall. An annular valve is coupled between the radially outer and the radially inner duct walls such that an outer bypass flow area is at least partially defined between the annular valve and the outer fairing, and such that an inner bypass flow area is at least partially defined between the annular valve and the inner fairing. The annular valve is selectively positioned between a first operational position and a second operational position, such that at least one of the outer bypass and the inner bypass flow areas is varied during a transition from a first turbine operation to a second turbine operation.Type: GrantFiled: May 25, 2007Date of Patent: November 23, 2010Assignee: General Electric CompanyInventors: Donald Michael Corsmeier, David Andrew Perveiler, George Joseph Johnson
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Publication number: 20100257841Abstract: A nozzle for use in a gas turbine engine includes a nozzle door having a first end, a second end opposed from the first end, and a pivot between the first end and the second end. A linkage connects to the nozzle door and to an actuator. The actuator is selectively operative to move the linkage to in turn move the nozzle door about the pivot between a plurality of positions, such as a stowed position, an intermediate position, and a thrust reverse position, to influence a bypass airflow through a fan bypass passage.Type: ApplicationFiled: March 29, 2007Publication date: October 14, 2010Inventors: Edward B. Pero, Leonard D. Aceto
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Patent number: 7805924Abstract: The present invention provides a mixer assembly including a mixer and a plurality of scoops attached around a circumference of the mixer element via a combination of sliding brackets and fixed brackets. The sliding brackets provide attachment and allow relative movement between the plurality of scoops and the mixer element while the fixed brackets provide only attachment between the mixer element and the plurality of scoops. The first sliding bracket includes a first flange that is fixedly mounted to the mixer element and a second flange that is biased against a surface of the scoop. A second sliding bracket is fixedly mounted to the mixer element and adjustably mounted to the scoop. The second sliding bracket includes an attachment hole and the scoop includes an adjustment slot. A fastener assembly including a spacer is received within the adjustment hole and the adjustment slot to allow relative movement between the mixer element and the scoop.Type: GrantFiled: November 30, 2006Date of Patent: October 5, 2010Assignee: United Technologies CorporationInventors: Adeyemi E. Alade, Paul W. Palmer
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Publication number: 20100236216Abstract: A turbofan engine (10) employs a flow control device (41) that changes an effective exit nozzle area (40) associated with a bypass flow path (B) of the turbofan engine. A spool (14) couples a fan (20) to a generator (52). The turbofan emergency power system includes a controller (50) that communicates with the flow control device (41). Upon sensing an emergency condition, the controller manipulates the flow control device to reduce the effective nozzle exit area (40) of the bypass flow path, which chokes the flow through the bypass flow path thereby increasing the rotational speed of the fan. In this manner, the generator is driven at a higher rotational speed than if the flow through the bypass flow path was not choked, which enables a smaller generator to be utilized.Type: ApplicationFiled: October 12, 2006Publication date: September 23, 2010Inventors: Michael Winter, Charles E. Lents
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Publication number: 20100229527Abstract: A variable area fan nozzle assembly for a turbofan engine includes a nacelle having an aft edge and a translating nozzle segment having a forward edge and a first end. The nozzle segment is movably disposed behind the aft edge such that an upstream bypass flow exit is defined between the aft edge and the forward edge when the nozzle segment is in a deployed position. A deflector is disposed between the aft edge and the forward edge proximate to the first end. The deflector substantially prevents bypass flow from exiting the upstream bypass flow exit in a region that is proximate to the first end.Type: ApplicationFiled: June 16, 2009Publication date: September 16, 2010Applicant: Rohr, Inc.Inventors: Daniel M. Amkraut, Michael John Layland, Norman John James
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Publication number: 20100199633Abstract: A bleed structure for a bleed passage in a gas turbine engine includes a first wall portion defining a first side of an opening for the passage, and a second wall portion defining a second side, opposite the first side of the opening. The first and second wall portions end at different positions in an extension direction of the opening.Type: ApplicationFiled: April 1, 2010Publication date: August 12, 2010Applicant: VOLVO AERO CORPORATIONInventors: Hans Martensson, Martin Nilsson
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Patent number: 7770381Abstract: A gas turbine engine includes a turbomachinery core operable to generating a first flow of pressurized combustion gases, the core having an exit plane; a fan disposed upstream of the core adapted to extract energy from the core and generate a first flow of pressurized air; a bypass duct surrounding the core which receives a portion of the flow of pressurized air from the fan; a duct burner disposed in the bypass duct, upstream of the exit plane, for receiving the first flow of pressurized air and generating a second flow of pressurized combustion gases; and an exhaust duct disposed downstream of the core and operable to receive and the first and second flows of pressurized combustion gases and to discharge the combined flows downstream.Type: GrantFiled: December 18, 2006Date of Patent: August 10, 2010Assignee: General Electric CompanyInventors: James E. Johnson, Ronald B. Steinmetz
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Patent number: 7762057Abstract: An aircraft includes at least one turbofan engine assembly having a shrouded core engine, a short nacelle surrounding a fan and a forward portion of the core engine, and a fan exhaust duct through the nacelle. A mixer duct shell is positioned substantially coaxial with the engine shroud and extends forwardly into the fan duct to provide an interstitial mixer duct between the mixer duct shell and the core engine shroud. The aft portion of the mixer duct shell extends over a turbine exhaust frame, an attached mixer (if included), and a tail cone exhaust plug. The mixer duct shell can reduce noise and plume exhaust heat radiated from aircraft turbofan engines.Type: GrantFiled: June 5, 2007Date of Patent: July 27, 2010Assignee: The Boeing CompanyInventors: Mark L. Sloan, Edward C. Marques, Matthew D. Moore, William J. Bigbee-Hansen
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Publication number: 20100180574Abstract: A gas turbine engine is disclosed which comprises a bypass duct, a core engine, and a fluid mixing arrangement. The fluid mixing arrangement is configured to mix a bypass flow of fluid and a secondary flow of fluid, the secondary flow of fluid being drawn from the core engine. The arrangement comprises a flow-duct terminating with an outlet and being arranged to direct said secondary flow through the outlet and into the bypass flow. The arrangement is characterised by the provision of a delta-shaped wing in the region of the outlet, said wing extending at least partially across the duct and being configured to generate lift from said secondary flow effective to produce at least one trailing vortex extending into said bypass flow. The fluid mixing arrangement can be used as a ventilation arrangement or as part of a bleed valve arrangement in the gas turbine engine.Type: ApplicationFiled: December 31, 2009Publication date: July 22, 2010Applicant: ROLLS-ROYCE PLCInventor: SATISH CHRISTOPH KHAKHAR
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Publication number: 20100180573Abstract: A gas turbine engine is proposed which comprises a bypass duct, a core engine, and a fluid mixing arrangement. The fluid mixing arrangement is configured to mix a bypass flow of fluid and a secondary flow of fluid, the secondary flow of fluid being drawn from the core engine. The arrangement comprises a flow duct terminating with an outlet and being arranged to direct said secondary flow through the outlet and into the bypass flow. The arrangement is characterised by the provision of a wing in the region of the outlet, said wing extending at least partially across the duct and being configured to generate lift from said secondary flow effective to produce at least one trailing vortex extending into said bypass flow. The fluid mixing arrangement can be used as a ventilation arrangement or as part of a bleed valve arrangement in the gas turbine engine.Type: ApplicationFiled: December 29, 2009Publication date: July 22, 2010Applicant: ROLLS-ROYCE PLCInventor: Simon Mark RUSTON
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Publication number: 20100170220Abstract: A gas turbine engine system includes a fan bypass passage (27), a core nacelle (28) having an inner fixed structure (40) within the fan bypass passage, a passage (42) extending through the inner fixed structure, and a duct nozzle (48). The passage includes an inlet (44) for receiving a fan airflow (F2) from the fan bypass passage and an outlet (46) for discharging the fan airflow. The duct nozzle includes a variable cross-sectional exit area (50) for controlling the fan airflow within the passage and is selectively moveable to influence the variable cross-sectional exit area.Type: ApplicationFiled: October 12, 2006Publication date: July 8, 2010Inventor: Gregory A. Kohlenberg
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Publication number: 20100170221Abstract: A turbo fan engine is equipped with a main body portion that has a high-pressure turbine and a low-pressure turbine, an output portion that is provided separately from the main body portion, a gas flow channel that communicates with a space between the high-pressure turbine and the low-pressure turbine and is connected to the output portion, and a flow rate adjustment portion that is provided in the gas flow channel to adjust a flow rate of a gas flowing through the gas flow channel.Type: ApplicationFiled: January 12, 2010Publication date: July 8, 2010Applicant: Toyota Jidosha Kabushiki KaishaInventors: Tadafumi Yoshida, Hiroki Tashiro
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Publication number: 20100162684Abstract: A nozzle is provided that can be used as part of an aircraft engine. In one form the nozzle includes an inner cowl and an outer cowl. The inner cowl can be actuated to a variety of positions. The outer cowl is piggybacked on the inner cowl and is initially retained in first position relative to the inner cowl with an outer cowl actuator. The outer cowl actuator can be commanded to release the outer cowl so that the outer cowl can be moved to a second position relative to the inner cowl. In one form the outer cowl actuator is an explosive bolt and a spring is provided to urge the outer cowl to the second position.Type: ApplicationFiled: November 30, 2009Publication date: July 1, 2010Inventor: Von David Baker
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Publication number: 20100162683Abstract: A turbofan engine is provided that includes a fan nacelle surrounding a core nacelle. The core nacelle houses a spool. The fan and core nacelles provide a bypass flow path having a nozzle exit area. A turbofan is arranged within the fan nacelle upstream from the core nacelle. A flow control device is adapted to effectively change the nozzle exit area to obtain a desired operating condition for the turbofan engine. A gear train couples the spool and turbofan for reducing a turbofan rotational speed relative to a spool rotational speed. A controller is programmed to respond to at least one sensor. The controller is programmed to effectively control the nozzle area.Type: ApplicationFiled: October 12, 2006Publication date: July 1, 2010Inventors: Zbigniew M. Grabowski, William J. McVey